Braking system architecture for aircraft

ABSTRACT

A braking system architecture for aircraft, the architecture comprising: a brake including friction members and electromechanical actuators for exerting a braking torque on the wheel; a computer situated in the fuselage of the aircraft and arranged to produce first control signals; and a junction box situated on the undercarriage, the junction box being connected to the computer and to the electromechanical actuators, the junction box being configured to receive the first control signals and to use the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators.

TECHNICAL FIELD

Embodiments of the present disclosure relate to the field of brakingsystem architectures for aircraft.

BACKGROUND

With reference to FIG. 1, a known centralized architecture for anelectric aircraft braking system comprises a plurality of brakes 1, eachserving to brake a wheel of an undercarriage of the aircraft.

Each brake 1 has four electromechanical braking actuators 2, which aregrouped together in two distinct groups of two electromechanicalactuators 2. The two electromechanical actuators 2 of each distinctgroup are connected to the same computer 3 situated in the fuselage ofthe aircraft, above the undercarriage.

The electric motor of each electromechanical actuator 2 receivesthree-phase electrical power from the computer 3 to which theelectromechanical actuator 2 is connected, and each electromechanicalactuator 2 transmits measurements of a servo-control parameter to thecomputer 3, e.g. measurements of the angular position of the rotor ofthe electric motor. The computers 3 implement functions of monitoringand controlling the electromechanical actuators 2, and also functions ofgenerating power by making use of inverters.

It can be seen that that centralized architecture requires the use of atleast ten electric wires per electromechanical actuator 2: three powersupply wires 4 for the three phases for powering the electric motor,four communication wires 5 for returning the measurements of the angularposition of the rotor of the electric motor to a centralized computer 3,and two power supply wires and a ground wire (not shown in FIG. 1) forcontrolling a member that blocks the electromechanical actuator 2 so asto act as a parking brake.

These electric wires are integrated in harnesses that run from thefuselage of the aircraft to the brake 1 and that are therefore bulky andheavy. The long length of the harnesses conveying the power supply wires4 (and thus conveying the currents powering the electric motors)requires the computers 3 to incorporate common mode filter circuits. Thefilter circuits add weight, complexity, and cost to the computers 3 andthus to the braking system.

SUMMARY

In accordance with an aspect of the present disclosure, a braking systemarchitecture for aircraft is provided. In an embodiment, thearchitecture comprises:

a brake for braking a wheel of an undercarriage of the aircraft, thebrake including friction members and electromechanical actuators forapplying a braking force against the friction members and therebyexerting a braking torque on the wheel;

a computer situated in the fuselage of the aircraft and arranged toproduce first control signals; and

a junction box situated on the undercarriage, the junction box beingconnected to the computer and to the electromechanical actuators, thejunction box being arranged to receive the first control signals, thejunction box is configured to use the first control signals to producesecond control signals for application to the electromechanicalactuators in order to control the electromechanical actuators. In anembodiment, the junction box employs electrical processor means forusing the first control signals to produce second control signals forapplication to the electromechanical actuators in order to control theelectromechanical actuators.

Using the junction box makes it possible to mutualize generating thesecond control signals from the first control signals, thereby reducingthe number of cables extending from the fuselage of the aircraft to thebrake. The number of components for performing functions is alsoreduced, since they can be mutualized in the junction box, therebyreducing the weight and the complexity of the braking system, andimproving its reliability.

DESCRIPTION OF THE DRAWINGS

The foregoing aspects and many of the attendant advantages of theclaimed subject matter will become more readily appreciated as the samebecome better understood by reference to the following detaileddescription, when taken in conjunction with the accompanying drawings,wherein:

FIG. 1 shows a prior art braking system architecture;

FIG. 2 shows a braking system architecture according to a firstembodiment of the disclosure;

FIG. 3 shows a braking system architecture according to a secondembodiment of the disclosure;

FIG. 4 shows a braking system architecture according to a thirdembodiment of the disclosure;

FIG. 5 shows a braking system architecture according to a fourthembodiment of the disclosure;

FIG. 6 shows a braking system architecture according to a fifthembodiment of the disclosure; and

FIG. 7 shows a braking system architecture according to a sixthembodiment of the disclosure.

DETAILED DESCRIPTION

The detailed description set forth below in connection with the appendeddrawings, where like numerals reference like elements, is intended as adescription of various embodiments of the disclosed subject matter andis not intended to represent the only embodiments. Each embodimentdescribed in this disclosure is provided merely as an example orillustration and should not be construed as preferred or advantageousover other embodiments. The illustrative examples provided herein arenot intended to be exhaustive or to limit the claimed subject matter tothe precise forms disclosed.

In these examples, embodiments are implemented on an aircraft that has aplurality of main undercarriages, each carrying a plurality of “braked”wheels, i.e. a plurality of wheels each fitted with a brake for brakingthe aircraft. The present disclosure relates to a single braked wheel;however the disclosure naturally applies in the same manner to all orsome of the braked wheels of the aircraft.

With reference to FIG. 2, a braking system architecture for aircraftaccording to a first embodiment of the disclosure includes a brake 100for braking a wheel of the aircraft, a computer 101, and a junction box102. The brake 100 includes four electromechanical braking actuators 103(only two electromechanical actuators 103 are shown in FIG. 2). Thecomputer 101, which is integrated in an avionics network, is positionedin a bay situated in the fuselage of the aircraft. The junction box 102is situated on the undercarriage, close to the brake. The junction box102 includes electrical processor means 105 comprising a digital switch,for example.

The computer 101 and the junction box 102 are connected together by afirst digital bus 106 having a first number of wires. The junction box102 is connected to each electromechanical actuator 103 by a seconddigital bus 107 having a second number of wires.

In addition to the four electromechanical actuators 103, the brake 100includes an actuator-carrier on which there are mounted the fourelectromechanical actuators 103 and friction members, for example, astack of carbon disks. The four electromechanical actuators 103 are usedto apply a braking force against the stack of carbon disks and therebyexert a braking torque on the wheel, slowing down rotation of the wheel,and thus braking the aircraft when it is on the ground.

Each electromechanical actuator 103 includes a body fastened to theactuator-carrier, a pusher, and a blocking member adapted to block thepusher in position. An electric motor, a power module 108, and a digitalcommunication module 109 are associated with or integrated inside thebody of each electromechanical actuator 103. The pusher is actuated bythe electric motor in order to slide and apply the braking force againstthe stack of carbon disks.

The power module 108 serves to generate alternating current (AC) powerthat flows in the three phases of the electric motor when it isappropriate to actuate the pusher and thus brake the wheel, and when itis appropriate to withdraw the pusher in order to stop braking thewheel. For this purpose, the power module 108 in some embodimentsincludes an inverter comprising a plurality of switches that arecontrolled so as to transform a direct current (DC) power supply voltageinto a three-phase AC voltage used for generating the power supply forthe electric motor.

The DC power supply voltages received by the power modules 108 of thefour electromechanical actuators 103 of the brake 100 come from one ormore power supply units situated in the fuselage of the aircraft, andnot shown in FIG. 2.

The computer 100 is configured to produce first control signals. Thejunction box 102 is configured and arranged to receive the first controlsignals and to produce second control signals. For example, theelectrical processor means 105 of the junction box are configured andarranged to use the first control signals to produce second controlsignals for application to the electromechanical actuators 103 in orderto control of the electromechanical actuators 103.

In this example, the first control signals and the second controlsignals comprise digital control signals for the electric motors of theelectromechanical actuators 103. The digital control signals, asproduced by the computer 100, are distributed to the digitalcommunication modules 109 of the electromechanical actuators 103 via thedigital switch of the electrical processor means 105 of the junction box102.

The digital communication module 109 of each mechanical actuator 103transforms the digital control signals that are sent thereto intoinverter control signals and transmits the inverter control signals tothe power module 108 and thus to the inverter of the power module 108.The inverter control signals control the switches of the inverter.

The digital communication modules 109 of the four electromechanicalactuators 103, and the digital switch of the electrical processor means105 of the junction box 102 are thus interconnected in order to form adigital network.

It should be observed that digital signals may also be returned from thewheel to the computer 101 and thus to the avionics network, via thesecond digital buses 107 and the first digital bus 106. The seconddigital buses 107 and the first digital bus 106 are thus bidirectionalbuses.

By way of example, the digital signals comprise digital measurementsignals produced by a data concentrator situated on the wheel. The dataconcentrator itself receives analog measurement signals produced bysensors situated on the wheel, and it generates the digital measurementsignals on the basis of the analog digital signals. The sensors measureparameters representative of a state of the wheel, e.g. a temperature ofthe brake, a pressure of the tire of the wheel, etc.

The digital signals may also comprise digital measurement signalsproduced by sensors associated with the electric motors of theelectromechanical actuators 103. These digital measurement signals serveto monitor the electrical motors of the electromechanical actuators. Byway of example, the sensors associated with the electric motors of themechanical actuators 103 measure angular positions or speeds of therotors of the electric motors, the power supply currents consumed by theelectric motors, etc.

It should be observed at this point that a junction box situated on theundercarriage is conventionally present in traditional braking systemarchitectures. The usual role of the junction box is to take cablingcoming from a harness running along the length of the undercarriage anddistribute it to each of the electromechanical actuators in order todeliver their power supply voltages to the electromechanical actuators.

In the present disclosure, the existing junction box is thus providedwith additional functions that are novel and innovative in order toobtain the junction box 102 without significantly modifying themechanical interfaces of an existing junction box. These functions donot require additional equipment, since the junction box is present intraditional architectures.

With reference to FIG. 3, a braking system architecture for aircraftaccording to a second embodiment of the disclosure includes a brake 200for braking a wheel of the aircraft, a computer 201, and a junction box202. The brake 200 includes four electromechanical braking actuators203. The computer 201, which is integrated in an avionics network, ispositioned in a bay situated in the fuselage of the aircraft.

The junction box 202 is situated on the undercarriage, close to thebrake 200. The junction box 202 includes first electrical processormeans 204 and second electrical processor means 205. The firstelectrical processor means 204 are arranged to perform a function ofmonitoring and controlling the electric motors of the fourelectromechanical actuators 203. The second electrical processor means205 are arranged to perform a function of monitoring and controlling theelectric motors of the four electromechanical actuators 203.

The computer 201 and the junction box 202 are connected together by afirst harness 206 having a first number of wires. The first harness 206includes a first digital bus. The junction box 202 is connected to eachelectromechanical actuator 203 by a second harness 207 having a secondnumber of wires. Each second harness 207 includes a second digital bus.

Each electromechanical actuator 203 includes a body fastened to theactuator-carrier, a pusher, and a blocking member adapted to block thepusher in position. An electric motor, a power module 208, a firstdigital communication module 209, and a second digital communicationmodule 210 are associated with or integrated inside the body of eachelectromechanical actuator 203.

The power module 208 serves to generate AC power that flows in the threephases of the electric motor when it is appropriate to actuate thepusher and thus brake the wheel, and when it is appropriate to withdrawthe pusher in order to stop braking the wheel. For this purpose, thepower module 203 includes, for example, an inverter comprising aplurality of switches that are controlled so as to transform a DC powersupply voltage into a three-phase AC voltage used for generating thepower supply for the electric motor.

The power supply voltages received by the power modules 208 of the fourelectromechanical actuators 203 of the brake come from one or more powersupply units situated in the fuselage of the aircraft, and not shown inFIG. 3.

The computer 201 is configured to produce first control signals. Thejunction box 202 is configured and arranged to receive the first controlsignals and to produce second control signals. For example, the firstelectrical processor means 204 and the second electrical processor means205 of the junction box 202 are configured and arranged to use the firstcontrol signals to produce second control signals for application to theelectromechanical actuators 203 in order to control of theelectromechanical actuators 203.

In this example, the first control signals comprise digital brakingcontrol signals. In this example, the second control signals comprisedigital control signals for the electric motors of the electromechanicalactuators.

The first electrical processor means 204 of the junction box 202 thususe the digital braking control signals to generate digital controlsignals for the electric motors of the electromechanical actuators 203for the first digital communication module 209 of each electromechanicalactuator 203.

The second electrical processor means 205 of the junction box 202 thususe the digital braking control signals to generate digital controlsignals for the electric motors of the electromechanical actuators 203for the second digital communication module 210 of eachelectromechanical actuator 203.

The first digital communication module 209 and the second digitalcommunication module 210 of an electromechanical actuator 203 transmitinverter control signals to the power module 208 and thus to theinverter of the power module 208 of the electromechanical actuator 203,which inverter control signals are generated from the digital controlsignals for the electric motors. The inverter control signals controlthe switches of the inverter.

It should be observed that the use of first electrical processor means204 and of second electrical processor means 205 in the junction box202, and of the first digital communication module 209 and of the seconddigital communication module 210 in each electromechanical actuator 203,makes it possible in a simple manner to obtain two dissimilar controlpaths, without multiplying the number of components and without thedesign of the components being too complex. The braking systemarchitecture in the second embodiment of the disclosure thus presentshigh levels of safety and reliability.

With reference to FIG. 4, a braking system architecture for aircraftaccording to a third embodiment of the disclosure includes a brake 300for braking a wheel of the aircraft, a computer 301, and a junction box302. The brake 300 includes four electromechanical braking actuators303. The computer 300, which is integrated in an avionics network, ispositioned in a bay situated in the fuselage of the aircraft.

The junction box 302 is situated on the undercarriage, close to thebrake. The junction box 302 includes first electrical processor means304 and second electrical processor means 305. The first electricalprocessor means 304 comprise a first digital-to-analog converter. Thesecond electrical processor means 305 comprise a seconddigital-to-analog converter.

The computer 300 and the junction box 302 are connected together by afirst harness 306 having a first number of wires. The junction box 302is connected to each electromechanical actuator 303 by a second harness307.

Each electromechanical actuator 303 includes a body fastened to theactuator-carrier, a pusher, and a blocking member adapted to block thepusher in position. An electric motor and a module 308 are associatedwith or integrated inside the body of each electromechanical actuator303.

The power module 308 serves to generate AC power that flows in the threephases of the electric motor when it is appropriate to actuate thepusher and thus brake the wheel, and when it is appropriate to withdrawthe pusher in order to stop braking the wheel. For this purpose, thepower module 308 includes an inverter comprising a plurality of switchesthat are controlled so as to transform a DC power supply voltage into athree-phase AC voltage used for generating the power supply for theelectric motor.

The power supply voltages received by the power modules 308 of the fourelectromechanical actuators 303 of the brake come from one or more powersupply units situated in the fuselage of the aircraft, and not shown inFIG. 4.

The computer 301 is configured to produce first control signals. Thejunction box 302 is configured and arranged to receive the first controlsignals and to produce second control signals. For example, the firstelectrical processor means 304 and the second electrical processor means305 of the junction box 302 are configured and arranged to use the firstcontrol signals to produce second control signals for application to theelectromechanical actuators 303 in order to control of theelectromechanical actuators 303.

In this example, the first control signals comprise digital controlsignals for the electric motors of the electromechanical actuators 303.In this example, the digital control signals implement a controlfunction by pulse width modulation.

The digital control signals, produced by the computer 301 aretransmitted to the first electrical processor means 304 and to thesecond electrical processor means 305. The first digital-to-analogconverter of the first electrical processor means 304 converts thedigital control signals into analog signals for controlling theinverter. The second digital-to-analog converter of the secondelectrical processor means 305 also converts the digital control signalsinto analog signals for controlling the inverter. In this example, thesecond control signals thus comprise the analog control signals for theinverter.

The power module 308 of each electromechanical actuator 303 thusreceives the analog inverter control signals and controls the inverterof the power module 308 by these analog inverter control signals.

Advantageously, the first electrical processor means 304 include a firstanalog-to-digital converter, and the second electrical processor means305 include a second analog-to-digital converter. The analog measurementsignals may be analog measurement signals produced by sensors situatedon the wheel, or analog measurement signals produced by sensorsassociated with the electric motors of the electromechanical actuators303. By way of example, the sensors associated with the electric motorsof the mechanical actuators 303 measure angular positions or speeds ofthe rotors of the electric motors, or else the power supply currentsconsumed by the electric motors.

With reference to FIG. 5, a braking system architecture for aircraftaccording to a fourth embodiment of the disclosure includes a brake 400for braking a wheel of the aircraft, a computer 401, and a junction box402. The brake includes four electromechanical braking actuators 403.The computer 401, which is integrated in an avionics network, ispositioned in a bay situated in the fuselage of the aircraft.

The junction box 402 is situated on the undercarriage, close to thebrake 400. The junction box 402 includes first electrical processormeans 404 and second electrical processor means 405. The firstelectrical processor means 404 are configured and arranged to perform abraking control function. The second electrical processor means 405 arealso configured and arranged to perform a braking control function.

The computer 401 and the junction box 402 are connected together by afirst harness 406 having a first digital bus. The junction box 402 isconnected to each electromechanical actuator 403 by a second harness 407having a second digital bus.

Each electromechanical actuator 403 includes a body fastened to theactuator-carrier, a pusher, and a blocking member adapted to block thepusher in position. An electric motor, a power module 408, a firstdigital communication module 409, and a second digital communicationmodule 410 are associated with or integrated inside the body of eachelectromechanical actuator 403.

The power module 408 serves to generate AC power that flows in the threephases of the electric motor when it is appropriate to actuate thepusher and thus brake the wheel, and when it is appropriate to withdrawthe pusher in order to stop braking the wheel. For this purpose, thepower module 408 includes an inverter comprising a plurality of switchesthat are controlled so as to transform a DC power supply voltage into athree-phase AC voltage used for generating the power supply for theelectric motor.

The power supply voltages received by the power modules 408 of the fourelectromechanical actuators 403 of the brake 400 come from one or morepower supply units situated in the fuselage of the aircraft, and notshown in FIG. 5.

The computer 401 is configured to produce first control signals. Thejunction box 402 is arranged to receive the first control signals and toproduce second control signals. For example, the first electricalprocessor means 404 and the second electrical processor means 405 of thejunction box 402 are configured and arranged to use the first controlsignals to produce second control signals for application to theelectromechanical actuators 403 in order to control of theelectromechanical actuators 403.

In this example, the first control signals comprise a braking setpoint.The first electrical processor means 404 of the junction box 402transform the braking setpoint into digital braking control signals. Thesecond electrical processor means 405 of the junction box 402 transformthe braking setpoint into digital braking control signals. In thisexample, the second control signals thus comprise digital brakingcontrol signals.

The first digital communication module 409 and the second digitalcommunication module 410 acquire the digital braking control signals,and each of them performs a function of monitoring and controlling theelectric motor. The monitoring and control function produces invertercontrol signals from the digital braking control signals. The invertercontrol signals control the switches of the inverter.

It should be observed that the use of first electrical processor means404 and of second electrical processor means 405 in the junction box402, and the use of the first digital communication module 409 and ofthe second digital communication module 410 in each electromechanicalactuator 403, makes it possible in a simple manner to obtain twodissimilar control paths, without multiplying the number of componentsand without the design of the components being too complex. The brakingsystem architecture in the fourth embodiment of the disclosure thuspresents high levels of safety and reliability.

With reference to FIG. 6, a braking system architecture for aircraftaccording to a fifth embodiment of the disclosure includes a brake 500for braking a wheel of the aircraft, a computer 501, and a junction box502. The brake includes four electromechanical braking actuators 503.The computer 501, which is integrated in an avionics network, ispositioned in a bay situated in the fuselage of the aircraft.

The junction box 502 is situated on the undercarriage, close to thebrake 500. The junction box 502 includes electrical processor meanscomprising four power converters 504. Each power converter 504 comprisesan inverter.

The computer 501 and the junction box 502 are connected together by afirst harness 506. The junction box 502 is connected to eachelectromechanical actuator 503 by a second harness 507.

Each electromechanical actuator 503 includes a body fastened to theactuator-carrier, a pusher, and a blocking member adapted to block thepusher in position. An electric motor is associated with or integratedinside the body of each electromechanical actuator 503.

The computer 501 is configured to produce first control signals. Thejunction box 502 is configured and arranged to receive the first controlsignals and to produce second control signals. For example, theelectrical processor means of the junction box 502 are configured andarranged to use the first control signals to produce second controlsignals for application to the electromechanical actuators 503 in orderto control of the electromechanical actuators.

The first control signals comprise a DC power supply voltage generatedby the computer 503 and transmitted to the junction box 502 via thefirst harness 506, together with inverter control signals. The DC powersupply voltage is generated by the computer 503 from an on-board powersupply source.

Each power converter 504 of the electrical processor means of thejunction box 502 uses the DC power supply voltage and the invertercontrol signals to generate power supply currents for the electric motorof one of the electromechanical actuators 503. The second controlsignals thus comprise power supply currents for the electric motors ofthe electromechanical actuators 503.

It should be observed that the braking system architecture in the fifthembodiment serves to simplify the cabling, by taking a DC power supplyvoltage to the junction box rather than a three-phase power supplyvoltage.

With reference to FIG. 7, a braking system architecture for aircraftaccording to a sixth embodiment of the disclosure includes a brake 600for braking a wheel of the aircraft, a computer 601, and a junction box602. The brake includes four electromechanical braking actuators 603.The computer 601, which is integrated in an avionics network, ispositioned in a bay situated in the fuselage of the aircraft.

The computer 601 includes first electrical processor means 604. Thefirst electrical processor means 604 are configured and arranged toperform a braking control function.

The junction box 602 is situated on the undercarriage, close to thebrake 600. The junction box 602 includes second electrical processormeans 605 comprising a digital switch, for example.

The computer 601 and the junction box 602 are connected together by afirst harness 606 having a first digital bus. The junction box 602 isconnected to the electromechanical actuators 603 by second harnesses607, each having a second digital bus.

Each electromechanical actuator 603 includes a body fastened to theactuator-carrier, a pusher, and a blocking member adapted to block thepusher in position. An electric motor, a power module 608, a firstdigital communication module 609, and a second digital communicationmodule 610 are associated with or integrated inside the body of eachelectromechanical actuator 603.

The power module 608 serves to generate AC power that flows in the threephases of the electric motor when it is appropriate to actuate thepusher and thus brake the wheel, and when it is appropriate to withdrawthe pusher in order to stop braking the wheel. For this purpose, thepower module 608 includes an inverter comprising a plurality of switchesthat are controlled so as to transform a DC power supply voltage into athree-phase AC voltage used for generating the power supply for theelectric motor.

The power supply voltages received by the power modules 608 of the fourelectromechanical actuators 603 of the brake 600 come from one or morepower supply units situated in the fuselage of the aircraft, and notshown in FIG. 7.

The computer 601 receives a braking setpoint. The first electricalprocessor means 604 of the computer 601 transform the braking setpointinto digital braking control signals. The first electrical processormeans 604 produce first control signals. In this example, the firstcontrol signals comprise the digital braking control signals.

The junction box 602 is configured and arranged to receive the firstcontrol signals and to produce second control signals. For example, thesecond electrical processor means 605 of the junction box 602 areconfigured and arranged to use the first control signals to producesecond control signals for application to the electromechanicalactuators 603 in order to control of the electromechanical actuators603.

The digital braking control signals, as produced by the computer 601,are distributed to the first digital communication module 609 and to thesecond digital communication module 610 of each electromechanicalactuator 603 via the digital switch of the second electrical processormeans 605 of the junction box 602.

In this example, the second control signals thus comprise the digitalbraking control signals.

The first digital communication module 609 and the second digitalcommunication module 610 acquire the digital braking control signals,and each of them performs a function of monitoring and controlling theelectric motor. The monitoring and control function produces invertercontrol signals from the digital braking control signals. The invertercontrol signals control the switches of the inverter.

Embodiments of the disclosure are not limited to the particularembodiments described above, but on the contrary, cover any variantcoming within the ambit of the disclosure as defined by the claims.

In particular, it is perfectly possible to combine certain architectureswith one another. For example, it is possible to use an architecture inwhich the junction box has processor means that generate both thecontrol signals and the power supply phase currents for the electricmotors.

It is also perfectly possible to use not one junction box, but aplurality of junction boxes. For example, it is possible to use anarchitecture in which a first junction box is connected to a firstcomputer and to two first electromechanical actuators of the brake, anda second junction box is connected to a second computer and to twosecond electromechanical actuators of the brake.

In each architecture, it is possible to make provision for some numberof components that is different from the numbers described. For example,in the first embodiment, provision may be made for eachelectromechanical actuator to have two digital communication modules, orin the second embodiment, provision may be made for eachelectromechanical actuator to have only one digital communicationmodule, or indeed in the fifth embodiment, provision may be made for theprocessor means of the junction box to have two power converters, etc.

The present description relates to a certain number of functionsperformed in the junction box, and to a certain number of componentsintegrated in the junction box. This description is not limiting in anyway. The junction box could perform other functions (e.g. filtering,measuring, monitoring, etc. functions), and could include othercomponents (e.g. filter components, sensors, etc.).

It should be observed that the computer mentioned herein may bepositioned at any location within the fuselage of the aircraft. By wayof example, the computer may be positioned in an avionics bay or closeto the cockpit of the aircraft. In particular, with an architecture inaccordance with the fourth embodiment of the disclosure, the computercould perfectly well be a “pedal box” that receives braking informationfrom the pilot and that transforms it into a braking setpoint that istransmitted to the junction box.

In some embodiments disclosed herein, the electrical processor meansincludes circuitry for implementing the functionality described in thevarious embodiments herein. The electrical processor means in someembodiments includes an electrical processor for implementing thefunctionality described herein. In some of these embodiments, theelectrical processor can be a digital switch, a digital to analogconverter, a power converter, among other electrical components. Some ofthe embodiments of the electrical processor means may include, forexample, logic for implementing the functionality described herein. Thislogic can be carried out by hardware, software, or a combination ofhardware and software. In some embodiments, the logic can be carried outby analog circuitry, digital circuitry, and combinations thereof. Insome embodiments, the logic can be carried out by a computer, a signalprocessor, a microprocessor, an ASIC, a field programmable gate array(FPGA), etc.

The principles, representative embodiments, and modes of operation ofthe present disclosure have been described in the foregoing description.However, aspects of the present disclosure which are intended to beprotected are not to be construed as limited to the particularembodiments disclosed. Further, the embodiments described herein are tobe regarded as illustrative rather than restrictive. It will beappreciated that variations and changes may be made by others, andequivalents employed, without departing from the spirit of the presentdisclosure. Accordingly, it is expressly intended that all suchvariations, changes, and equivalents fall within the spirit and scope ofthe present disclosure, as claimed.

The embodiments of the invention in which an exclusive property orprivilege is claimed are defined as follows:
 1. A braking systemarchitecture for aircraft, the architecture comprising: a brake forbraking a wheel of an undercarriage of the aircraft, the brake includingfriction members and electromechanical actuators for applying a brakingforce against the friction members and thereby exerting a braking torqueon the wheel; a computer situated in the fuselage of the aircraft andarranged to produce first control signals; and a junction box situatedon the undercarriage, the junction box being connected to the computerand to the electromechanical actuators, the junction box beingconfigured and arranged to receive the first control signals, thejunction box comprising electrical processor means configured andarranged to use the first control signals to produce second controlsignals for application to the electromechanical actuators in order tocontrol the electromechanical actuators.
 2. The architecture accordingto claim 1, wherein each electromechanical actuator includes a bodyhaving integrated therein an electric motor, a power module forgenerating a power supply current for the electric motor, and a digitalcommunication module, wherein the electrical processor means of thejunction box include a digital switch, and wherein the first controlsignals and the second control signals comprise digital signals forcontrolling the electric motors.
 3. The architecture according to claim1, wherein each electromechanical actuator includes a body havingintegrated therein an electric motor, a power module for generating apower supply current for the electric motor, and a digital communicationmodule, wherein the electrical processor means of the junction box areconfigured and arranged to perform a function of monitoring andcontrolling the electric motors, and wherein the first control signalscomprise digital braking control signals and the second control signalscomprise digital signals for controlling the electric motors.
 4. Thearchitecture according to claim 1, wherein each electromechanicalactuator includes a body having integrated therein an electric motor, apower module for generating a power supply current for the electricmotor, and a digital communication module, wherein the electricalprocessor means of the junction box include a digital-to-analogconverter, and wherein the first control signals comprise digitalsignals for controlling the electric motors and the second controlsignals comprise analog signals for controlling the electric motors. 5.The architecture according to claim 4, wherein the wheel or the electricmotors of the electromechanical actuators include a sensor adapted toproduce analog measurement signals of a parameter of the wheel or of theelectric motors, wherein the electrical processor means of the junctionbox include an analog-to-digital converter configured and arranged toconvert the analog measurement signals into digital measurement signals,and wherein the electrical processor means of the junction box areconfigured and arranged to transmit the digital measurement signals tothe computer.
 6. The architecture according to claim 1, wherein eachelectromechanical actuator includes a body having integrated therein anelectric motor, a power module for generating a power supply current forthe electric motor, and a digital communication module arranged toperform a function of monitoring and controlling the electric motor ofthe electromechanical actuator, wherein the electrical processor meansof the junction box are configured and arranged to perform a brakingcontrol function, and wherein the first control signals comprise abraking setpoint and the second control signals comprise digital brakingcontrol signals.
 7. The architecture according to claim 1, wherein eachelectromechanical actuator includes a body having integrated therein anelectric motor, wherein the electrical processor means of the junctionbox include power converters, and wherein the first control signalscomprise a power supply coming from an on-board power supply source andthe second control signals comprise power supply currents for theelectric motors.
 8. The architecture according to claim 1, wherein eachelectromechanical actuator includes a body having integrated therein anelectric motor, a power module for generating a power supply current forthe electric motor, and a digital communication module arranged toperform a function of monitoring and controlling the electric motor ofthe electromechanical actuator, wherein the electrical processor meansof the junction box are configured and arranged to perform a brakingcontrol function, and wherein the first control signals and the secondcontrol signals comprise digital braking control signals.
 9. A brakingsystem architecture for aircraft, the architecture comprising: a brakeconfigured to brake a wheel of an undercarriage of the aircraft, thebrake including friction members and electromechanical actuators forapplying a braking force against the friction members to exert a brakingtorque on the wheel; a computer situated in the fuselage of the aircraftand configured to produce first control signals; and a junction boxsituated on the undercarriage, the junction box being connected to thecomputer and to the electromechanical actuators, the junction box beingconfigured to receive the first control signals and to use the firstcontrol signals to produce second control signals for application to theelectromechanical actuators in order to control the electromechanicalactuators.
 10. The architecture according to claim 9, wherein thejunction box includes electrical processor means.
 11. The architectureaccording to claim 10, wherein the electrical processor means isselected from a group consisting of a digital switch, a digital toanalog converter, and a power converter.
 12. An aircraft, comprising: abrake configured to brake a wheel of an undercarriage of the aircraft,the brake including one or more electromechanical actuators; a computersituated in a fuselage of the aircraft and configured to produce firstcontrol signals; and a junction box situated on the undercarriage andelectrically connected to the computer and to the one or moreelectromechanical actuators, the junction box being configured toreceive the first control signals, the junction box comprising anelectrical processor configured to use the first control signals toproduce second control signals for application to the electromechanicalactuators in order to control the electromechanical actuators.
 13. Theaircraft according to claim 12, wherein each electromechanical actuatorincludes a body having integrated therein an electric motor, a powermodule for generating a power supply current for the electric motor, anda digital communication module, wherein the electrical processor includea digital switch, and wherein the first control signals and the secondcontrol signals comprise digital signals for controlling the electricmotor.
 14. The aircraft according to claim 12, wherein eachelectromechanical actuator includes a body having integrated therein anelectric motor, a power module for generating a power supply current forthe electric motor, and a digital communication module, wherein theelectrical processor is configured to monitor and control the electricmotors, and wherein the first control signals comprise digital brakingcontrol signals and the second control signals comprise digital signalsfor controlling the electric motors.
 15. The aircraft according to claim12, wherein each electromechanical actuator includes a body havingintegrated therein an electric motor, a power module for generating apower supply current for the electric motor, and a digital communicationmodule, wherein the electrical processor means of the junction boxinclude a digital-to-analog converter, and wherein the first controlsignals comprise digital signals for controlling the electric motors andthe second control signals comprise analog signals for controlling theelectric motors.
 16. The aircraft according to claim 15, wherein thewheel or the electric motors of the electromechanical actuators includea sensor adapted to produce analog measurement signals of a parameter ofthe wheel or of the electric motors, wherein the electrical processorincludes an analog-to-digital converter configured to convert the analogmeasurement signals into digital measurement signals, and wherein theelectrical processor is configured to transmit the digital measurementsignals to the computer.
 17. The aircraft according to claim 12, whereineach electromechanical actuator includes a body having integratedtherein an electric motor, a power module for generating a power supplycurrent for the electric motor, and a digital communication moduleconfigured to monitor and control the electric motor of theelectromechanical actuator, wherein the electrical processor isconfigured to perform a braking control function, and wherein the firstcontrol signals comprise a braking setpoint and the second controlsignals comprise digital braking control signals.
 18. The aircraftaccording to claim 12, wherein each electromechanical actuator includesa body having integrated therein an electric motor, wherein theelectrical processor includes one or more power converter, and whereinthe first control signals comprise a power supply coming from anon-board power supply source and the second control signals comprisepower supply currents for the electric motors.
 19. The aircraftaccording to claim 12, wherein each electromechanical actuator includesa body having integrated therein an electric motor, a power module forgenerating a power supply current for the electric motor, and a digitalcommunication module configured to perform a function of monitoring andcontrolling the electric motor of the electromechanical actuator,wherein the electrical processor means of the junction box areconfigured and configured to perform a braking control function, andwherein the first control signals and the second control signalscomprise digital braking control signals.